Abstract: An engine pylon that is used for supporting an engine, the engine pylon including a pylon body having an upper pylon and a lower pylon. The pylon further includes a fairing that covers the pylon body such that the upper pylon and fairing define a predetermined region. Moreover, the pylon includes a first drain that is configured to discharge a flammable liquid leaking from a pipe provided within the predetermined region into outside air; and a ventilation path configured to bring the inside of the predetermined region into communication with the outside air. The first drain includes a drain port and a drain pipe, wherein the drain pipe extends in a rear direction from the drain port and has an outlet at a rear end of the drain pipe, the outlet being located past a rear end of the upper pylon and a rear end of the lower pylon.

Abstract: An aircraft includes an accessory member that constitutes an engine accessory, the accessory member being arranged between an aircraft engine pylon and an engine, in an attached state to an attachment base member that is at least one of the pylon and the engine. The accessory member includes: a surrounding portion that surrounds at least an end portion of a tubular body connected to the accessory member; and a projecting portion that projects from the end portion of the tubular body. The entire accessory member including the surrounding portion and the projecting portion is divided so as to be separable to a left side and a right side of the pylon, and the accessory member is attachable to and detachable from the attachment base member by accessing an outer periphery of the tubular body from the left side and the right side of the pylon without removing another member.

Abstract: An aircraft including a turbofan engine provided with an engine body and a fan located anterior to the engine body, further includes: an engine oil cooler that is a heat exchanger for cooling engine oil used in the engine body by using, as a heat source, a fan stream flowing from the fan into a gap between a core cowl surrounding the engine body and a nacelle surrounding the fan and the core cowl; and a pre-cooler that is a heat exchanger for cooling bleed air from the engine body by using the fan stream as a heat source, wherein the engine oil cooler and the pre-cooler are longitudinally arranged in one position in a circumferential direction of the nacelle, and the engine oil cooler is located anterior to the pre-cooler.

Abstract: The present invention provides a method for mounting an aircraft engine, which enables to speed up a mounting work by facilitating positioning of an engine with respect to a pylon. The method for mounting an aircraft engine, including: lifting up an engine of an aircraft toward a pylon that is a mounting object; and when the engine reaches a predetermined position, fixing the engine to the pylon, wherein guides that perform horizontal positioning of the engine with respect to the pylon are respectively provided on a front side and a rear side of the engine.

Abstract: An aircraft with a turbofan engine including an engine body and a fan, wherein the turbofan engine is supported on an airframe via a pylon, an igniter cable is interposed between an ignition plug of the engine and an ignition control unit that controls power supply to the ignition plug, and at least a part of the igniter cable is passed through an inside of the pylon.

Abstract: An aircraft including a turbofan engine provided with an engine body and a fan located anterior to the engine body, further includes: an engine oil cooler that is a heat exchanger for cooling engine oil used in the engine body by using, as a heat source, a fan stream flowing from the fan into a gap between a core cowl surrounding the engine body and a nacelle surrounding the fan and the core cowl; and a pre-cooler that is a heat exchanger for cooling bleed air from the engine body by using the fan stream as a heat source, wherein the engine oil cooler and the pre-cooler are longitudinally arranged in one position in a circumferential direction of the nacelle, and the engine oil cooler is located anterior to the pre-cooler.

Abstract: The present invention provides a method for mounting an aircraft engine, which enables to speed up a mounting work by facilitating positioning of an engine with respect to a pylon. The method for mounting an aircraft engine, including: lifting up an engine of an aircraft toward a pylon that is a mounting object; and when the engine reaches a predetermined position, fixing the engine to the pylon, wherein guides that perform horizontal positioning of the engine with respect to the pylon are respectively provided on a front side and a rear side of the engine.

Abstract: An aircraft including a turbofan engine provided with an engine body and a fan located anterior to the engine body, further includes: an engine oil cooler that is a heat exchanger for cooling engine oil used in the engine body by using, as a heat source, a fan stream flowing from the fan into a gap between a core cowl surrounding the engine body and a nacelle surrounding the fan and the core cowl; and a pre-cooler that is a heat exchanger for cooling bleed air from the engine body by using the fan stream as a heat source, wherein the engine oil cooler and the pre-cooler are longitudinally arranged in one position in a circumferential direction of the nacelle, and the engine oil cooler is located anterior to the pre-cooler.

Abstract: An engine pylon of an aircraft that is used for supporting an engine of an aircraft on a main wing, the pylon including a first drain that discharges a flammable liquid leaking from a pipe provided within a predetermined region in the pylon into outside air from inside of the region; and a ventilation path that brings the inside of the region into communication with outside air.

Abstract: An aircraft includes an accessory member that constitutes an engine accessory, the accessory member being arranged between an aircraft engine pylon and an engine, in an attached state to an attachment base member that is at least one of the pylon and the engine. The accessory member includes: a surrounding portion that surrounds at least an end portion of a tubular body connected to the accessory member; and a projecting portion that projects from the end portion of the tubular body. The entire accessory member including the surrounding portion and the projecting portion is divided so as to be separable to a left side and a right side of the pylon, and the accessory member is attachable to and detachable from the attachment base member by accessing an outer periphery of the tubular body from the left side and the right side of the pylon without removing another member.

Abstract: An aircraft with a turbofan engine including an engine body and a fan, wherein the turbofan engine is supported on an airframe via a pylon, an igniter cable is interposed between an ignition plug of the engine and an ignition control unit that controls power supply to the ignition plug, and at least a part of the igniter cable is passed through an inside of the pylon.